FR2919347B1 - EXTERNAL ENVELOPE FOR BLOWER DRIVE IN A TURBOMACHINE. - Google Patents

EXTERNAL ENVELOPE FOR BLOWER DRIVE IN A TURBOMACHINE.

Info

Publication number
FR2919347B1
FR2919347B1 FR0705455A FR0705455A FR2919347B1 FR 2919347 B1 FR2919347 B1 FR 2919347B1 FR 0705455 A FR0705455 A FR 0705455A FR 0705455 A FR0705455 A FR 0705455A FR 2919347 B1 FR2919347 B1 FR 2919347B1
Authority
FR
France
Prior art keywords
turbomachine
casing
external envelope
blower drive
annular flange
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related
Application number
FR0705455A
Other languages
French (fr)
Other versions
FR2919347A1 (en
Inventor
Jacky Raphael Michel Derenes
Delphine Edith Dijoud
Sebastien Regard
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Priority to FR0705455A priority Critical patent/FR2919347B1/en
Priority to DE602008001217T priority patent/DE602008001217D1/en
Priority to EP08159832A priority patent/EP2022973B1/en
Priority to US12/177,369 priority patent/US8272203B2/en
Priority to CA2637647A priority patent/CA2637647C/en
Priority to JP2008190512A priority patent/JP2009030604A/en
Priority to RU2008130816/06A priority patent/RU2462601C2/en
Publication of FR2919347A1 publication Critical patent/FR2919347A1/en
Application granted granted Critical
Publication of FR2919347B1 publication Critical patent/FR2919347B1/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/183—Two-dimensional patterned zigzag
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/231—Three-dimensional prismatic cylindrical
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Abstract

Turboréacteur à double flux (10), comprenant une enveloppe cylindrique (20) délimitant extérieurement un espace annulaire d'écoulement d'un flux secondaire (28), caractérisé en ce que l'enveloppe cylindrique (20) est formée d'une ossature en treillis (30) et de panneaux de carénage amovibles (32) fixés sur l'ossature, celle-ci comprenant une bride annulaire amont (34) de fixation à un carter intermédiaire (16), une bride annulaire aval (36) de liaison à un carter d'échappement, et des poutres rigides (42, 46) parallèles ou inclinées par rapport à l'axe (44) du turboréacteur, reliant les deux brides (34, 36) entre elles.Turbofan engine (10), comprising a cylindrical casing (20) externally delimiting an annular flow space for a secondary flow (28), characterized in that the cylindrical casing (20) is formed of a trellis (30) and removable fairing panels (32) fixed to the framework, the latter comprising an upstream annular flange (34) for fixing to an intermediate casing (16), a downstream annular flange (36) for connection to an exhaust casing, and rigid beams (42, 46) parallel or inclined relative to the axis (44) of the turbojet, connecting the two flanges (34, 36) together.

FR0705455A 2007-07-26 2007-07-26 EXTERNAL ENVELOPE FOR BLOWER DRIVE IN A TURBOMACHINE. Expired - Fee Related FR2919347B1 (en)

Priority Applications (7)

Application Number Priority Date Filing Date Title
FR0705455A FR2919347B1 (en) 2007-07-26 2007-07-26 EXTERNAL ENVELOPE FOR BLOWER DRIVE IN A TURBOMACHINE.
DE602008001217T DE602008001217D1 (en) 2007-07-26 2008-07-07 Outer housing of a fan impeller in a turbomachine
EP08159832A EP2022973B1 (en) 2007-07-26 2008-07-07 Outer casing for a turbomachine fan conduit
US12/177,369 US8272203B2 (en) 2007-07-26 2008-07-22 External fan duct casing in a turbomachine
CA2637647A CA2637647C (en) 2007-07-26 2008-07-23 External wall of a fan conduit in a turbine engine
JP2008190512A JP2009030604A (en) 2007-07-26 2008-07-24 External fan duct casing in turbomachine
RU2008130816/06A RU2462601C2 (en) 2007-07-26 2008-07-25 External cover of air pipe of gas-turbine engine fan

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0705455A FR2919347B1 (en) 2007-07-26 2007-07-26 EXTERNAL ENVELOPE FOR BLOWER DRIVE IN A TURBOMACHINE.

Publications (2)

Publication Number Publication Date
FR2919347A1 FR2919347A1 (en) 2009-01-30
FR2919347B1 true FR2919347B1 (en) 2009-11-20

Family

ID=39171454

Family Applications (1)

Application Number Title Priority Date Filing Date
FR0705455A Expired - Fee Related FR2919347B1 (en) 2007-07-26 2007-07-26 EXTERNAL ENVELOPE FOR BLOWER DRIVE IN A TURBOMACHINE.

Country Status (7)

Country Link
US (1) US8272203B2 (en)
EP (1) EP2022973B1 (en)
JP (1) JP2009030604A (en)
CA (1) CA2637647C (en)
DE (1) DE602008001217D1 (en)
FR (1) FR2919347B1 (en)
RU (1) RU2462601C2 (en)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2933070B1 (en) * 2008-06-25 2010-08-20 Snecma PROPULSIVE AIRCRAFT SYSTEM
FR2952126B1 (en) * 2009-11-04 2011-12-23 Snecma DOUBLE FLOW TURBOMACHINE FOR AIRCRAFT, COMPRISING STRUCTURAL MEANS FOR RIGIDIFYING THE CENTRAL CARTER
FR2956164B1 (en) * 2010-02-10 2012-02-24 Snecma CONNECTION BETWEEN THE EXHAUST CASE AND A STRUCTURAL RING OF A BLOWER DELIVERY OF A TURBOREACTOR
FR2964415B1 (en) * 2010-09-08 2015-11-13 Snecma HYPERSTATIC MOTOR SUSPENSION TRELLIS
US9498850B2 (en) 2012-03-27 2016-11-22 Pratt & Whitney Canada Corp. Structural case for aircraft gas turbine engine
FR2988777B1 (en) * 2012-03-29 2014-04-25 Snecma Propulsion Solide INTEGRATION OF REAR BODY PARTS OF AERONAUTICAL MOTOR
FR3008136B1 (en) * 2013-07-04 2017-12-15 Snecma SUSPENSION OF A STRUCTURE IN A TURBOREACTOR BY A HYPERSTATIC MESH WITH PRE-TENSION BONDING ELEMENTS AND ASSOCIATED PRE-TENSIONING METHOD
GB201322077D0 (en) * 2013-12-13 2014-01-29 Rolls Royce Plc Engine mount
GB201418396D0 (en) * 2014-10-17 2014-12-03 Rolls Royce Plc Gas turbine engine support structures
DE102016101168A1 (en) * 2016-01-22 2017-07-27 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine with an arranged in a recess of a wall insertion device
DE102016101166A1 (en) * 2016-01-22 2017-07-27 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine with a frame structure having a wall
US10830097B2 (en) 2016-02-04 2020-11-10 General Electric Company Engine casing with internal coolant flow patterns
DE102016213810A1 (en) * 2016-07-27 2018-02-01 MTU Aero Engines AG Cladding element for a turbine intermediate housing
RU2689393C1 (en) * 2018-06-26 2019-05-28 Общество с ограниченной ответственностью "Профит Центр Плюс" Air duct for cooling system and ventilation of traction motors of locomotives
US11585274B2 (en) * 2020-12-28 2023-02-21 General Electric Company Turbine rear frame link assemblies for turbofan engines
CN115628151A (en) * 2022-12-06 2023-01-20 南京航空航天大学 Full-shielding flow guide supporting plate for turbofan engine

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB536461A (en) * 1939-12-20 1941-05-15 Fairey Aviat Co Ltd Improvements in or relating to means for securing removable panels and the like on aircraft fuselages and similar bodies
US2286908A (en) * 1940-08-07 1942-06-16 Robert H Goddard Auxiliary turbine for rocket craft
US2421689A (en) * 1944-10-09 1947-06-03 Lockheed Aircraft Corp Cowling arrangement
US3449914A (en) * 1967-12-21 1969-06-17 United Aircraft Corp Variable flow turbofan engine
US4266741A (en) * 1978-05-22 1981-05-12 The Boeing Company Mounting apparatus for fan jet engine having mixed flow nozzle installation
US4213585A (en) * 1978-05-22 1980-07-22 The Boeing Company Mounting system for a wing mounted aircraft engine
US4471609A (en) * 1982-08-23 1984-09-18 The Boeing Company Apparatus and method for minimizing engine backbone bending
FR2613773B1 (en) * 1987-04-08 1990-11-30 Snecma ACOUSTIC PANEL FOR SOUNDPROOFING AND TURBOREACTOR COMPRISING SUCH A TRIM
US5222360A (en) * 1991-10-30 1993-06-29 General Electric Company Apparatus for removably attaching a core frame to a vane frame with a stable mid ring
US5451116A (en) * 1992-06-09 1995-09-19 General Electric Company Tripod plate for turbine flowpath
GB2267736B (en) * 1992-06-09 1995-08-09 Gen Electric Segmented turbine flowpath assembly
DE69524883T2 (en) * 1994-10-13 2002-09-19 Boeing Co SYSTEM FOR REDUCING NOISE FROM A NOZZLE ENGINE BY MEANS OF ELECTROPNEUMATIC CONVERTERS
US6886343B2 (en) * 2003-01-15 2005-05-03 General Electric Company Methods and apparatus for controlling engine clearance closures
US7370467B2 (en) * 2003-07-29 2008-05-13 Pratt & Whitney Canada Corp. Turbofan case and method of making
US7318619B2 (en) * 2004-01-12 2008-01-15 Munro & Associates Method and apparatus for reducing drag and noise for a vehicle
FR2865001B1 (en) * 2004-01-12 2008-05-09 Snecma Moteurs TURBOREACTOR COMPRISING A SERVITUDE CONNECTING ARM AND THE SERVITUDE CONNECTING ARM.
FR2866070B1 (en) * 2004-02-05 2008-12-05 Snecma Moteurs TURBOREACTOR WITH HIGH DILUTION RATE
UA78810C2 (en) * 2005-01-24 2007-04-25 State Entpr Zaporizhia Academi Appliance for reversing propulsion of two-contour turbo-jet engine

Also Published As

Publication number Publication date
JP2009030604A (en) 2009-02-12
RU2008130816A (en) 2010-01-27
US8272203B2 (en) 2012-09-25
DE602008001217D1 (en) 2010-06-24
EP2022973B1 (en) 2010-05-12
US20100047066A1 (en) 2010-02-25
RU2462601C2 (en) 2012-09-27
CA2637647C (en) 2014-09-30
CA2637647A1 (en) 2009-01-26
EP2022973A1 (en) 2009-02-11
FR2919347A1 (en) 2009-01-30

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Legal Events

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ST Notification of lapse

Effective date: 20120330